72-00-00
AMM
Intentionally left blank
72-00-00
Engine
AMM
% Section 72-01 % TAE 125 Diesel Engine % 1. General
% This Section gives you background data about the TAE 125 Diesel engine installed in the DA 40 % airplane.
% Note: Ontly TAE authorized maintenance organizations may carry out maintenance and % inspection work on the TAE engine. Refer to TAE Service Bulletin No. 125-0003. % Any engine malfunction must be reported to TAE.
% 2. Description
% The TAE 125 is a liquid-cooled, 4-cylinder, 4-stroke in-line turbocharged engine with double overhead % camshafts. The engine has a direct-injection fuel system controlled by computers. A reduction gearbox % with a ratio of 1.69:1 turns the propeller. The gearbox has an integral torsional vibration damper with % an overload clutch. The engine has an electric starter and a generator.
% The TAE 125 engine operates on the Diesel cycle. The engine has a crankcase, crankshaft, cylinders, % pistons and valves like conventional piston aero-engines. However, there is no ignition system.
% In the Diesel engine, air is drawn into the cylinders and compressed to a high pressure. A high % pressure pump injects a metered quantity of fuel into the cylinder. The air is hot enough to ignite the % fuel. The fuel burns and expands the air to force the piston down the cylinder. The air pumping cycle % and valve operation is the same as in a conventional piston aero-engine.
% A Full Authority Digital Engine Control (FADEC) system controls the fuel system, propeller and turbo-% charger. The FADEC has 2 Engine Control Units (ECU's) located in a sealed unit under the pilot's % seat. Sensors located on the engine measure the engine parameters for the system. An electrical % harness connects the system components.
% The fuel injection pump supplies 4 injectors connected to a common high-pressure rail. The active % ECU controls the opening of each injector to inject the correct quantity of fuel for position of the % cockpit power lever.
% The TAE 125 has a turbo-charger to increase the efficiency and power output. Exhaust gases go % through a turbine before flowing through a conventional exhaust to atmosphere. A ‘Waste Gate’ % (bypass valve) in parallel with the turbine controls the volume of exhaust gas going through the % turbine. The turbine turns a centrifugal compressor. The compressor supplies air to the engine through % an intercooler.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003
72-01-00 72-01-00
Engine AIRCRAFT DA 40 Series AMM
%
%
% Engine Oil Filter Housing
%
%
%
%
%
% Engine Oil Filler
%
% Gearbox Oil
% Filler Plug
%
%
%
%
%
%
% Gearbox Oil Filter Cover
%
% Gearbox Oil
% Level Window
%
% % Gearbox Oil Drain Plug Engine Oil Drain Plug
%
%
% Figure 1: Oil System Maintenance Locations
%
Engine
AMM
% 3. Engine Oil System % The engine has the usual wet sump oil system. The sump has a maximum capacity of 6 liters (6.3 US % qts). Refer to the Airplane Flight Manual Chapter 2 for data about the oil types to use in the engine. % The oil pump supplies oil to all bearings and other components that require oil. Oil galleries inside the % engine crankcase and cylinder head supply oil to the internal components. % Figure 1 shows the location of the items that you can maintain on the engine oil system. The engine % has these maintenance locations: 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：钻石40飞机维护手册 DA 40 SERIES AMM 5(48)
